Turbo-compressor.



H. JUNKERS.

TURBO COMPRESSOR.

1 11101111011 rum) JUNE 13, 1911.

Patented Feb. 24, 1914.

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H. J UNKERS.

TURBO COMPRESSOR.

APPLICATION FILED JUNE 13, 1911.

Patented Feb. 24, 1914.

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TURBO OOMPRESSOR. APPLICATION FILED mm: 13, 1911.

1,088,585. Patented Feb..24,1914.

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HUoo JUNKERs, or AIx-LA-cHArELtE, GERMANY.

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To all whom it may concern Be it known that I, HUGO JUNKnRs, a subject of the King of Prussia, residing at No. 68 Bismarckstrasse, Aix-la-Ohapelle, in the Kingdom of Prussia, Empire of Germany, have invented certain new and useful Improvements in Turbo-Compressors; and I do hereby declare the following to be a full, clear, and exact description of the invention, such as will enable others skilled' in the art to which it appertains to make and use the-same.

My present invention relates to turbo-compressors and in particular to the coolingdevices used in connection with such ma-' chines. The devices of this kind hitherto employed for. obtaining an approximately isothermal compression were placed outside the Walls of the turbine casing, whereby the dimensions of the whole structure of such engines were unavoidably increased. The resistanceof the gases resulting from friction on the walls of the conduits, change of the direction of the gases, etc., caused con siderable losses of energy and a working of the engines in question in such economical manner as'made possible by the use of this proposed device has probably never been as ch known before. Owing to the above mentioned disadvantages a restricted number of cooling-devices could only be employedespecially for multi stage-turbi nesand for this reason an isothermal compression has never even approximately been: obtained by eseeompressors, and the energy ained by the coolingdevice's" represented on y avery small amount. According to the present invention these drawbacks are avoided by the use of so called indirect cooling-surfaces which are inserted in the channels provided .for the passage-of the gases in the interior of the turbine and arranged in such a manner that the gases passing with great velocity throu h the turbine are sliced up into layers. avorable conditions [are thus created for the transmission of heat and at the 7 same time a very large cooling-surface can be lodged in the turbine itself without perceptibly enlarging the casing of the turbine. The indirect cooling-surfaces consistof thin and good heat conducting cool1ng:plates which can be straight or curved as circumstances may require. Thejedges of the cooling plates are preferably wedge-she ed -1n order to ofier less resistance to the ow of the gases; The form of the cooling-plates Specification of Letters Patent. Application filed June 1a, 1913. Serial No. 632,941.

formed by t increase of resistances, etc.

Patented Feb. 24, 1914.

channels for the cooling-medium are kept very short and simple and pipe-couplings are, .as far as possible, dispensed with. An

other advantage gained by the arrangement described consists therein that the coolingplates may be adapted to suit the method of working of the different turbine-types avoiding thereby injurious losses resulting from change of the direction of the gases, whirls,

that the cooling-devices are placed in the casing ofthe turbine the great differences in the'cross sectional areas of the gas-passages, as for instance shown by nearly all types of cooling-devices now in'use do not occur by the use of the present invention. The great velocity of the gases passing through the different stages of the turbine can thus easily For the reason.

be maintained and may therefore be used to improve the transmissionof heat, as the latter depends onthe velocity of the gases.

Other objects and advantages will be fully explained in the following description and the invention will be more particularly pointed out inthe claims.

Reference isv had to the accompanying drawings which form a part of this application.

Similar characters of references are used to indicate the same parts throughout the several views.

Figure 1 represents a. part of a longitudi- I I nal sectional view of a centrifugal compressor; the cooling-device a being mounted in'th'einterior of the turbine. Fi 2 is 9.

plates d are connected on bot sides with the cooling-channel's e 'for the reception ofthe cooling-medium which is supplied to the cooling-channels e by a feeding-pipe f anddrawn ofi by another pi e 9. Fig. 3 shows the cooling-device lodged in a socalled diffuser k of a compressor. The cooling-plates are radially arranged to the axis cross sectional yiew of the device s mm} in Fig. -1. The radially arran ed coo11ng-' 105.

of the turbine. Fig. 4 is an end view of the cooling-device represented in Fig. 3. Figs. 5 and 6 illustrate an annular cooling-device placed around the circumference of the rotor 0. According to the inclined directions of the gases escaping from the rotor the cooling-plates are curved in order to avoidinjurious shocks. Figs. 7 and 8 show the E001- ing-device fitted between the stages of an aXial-flow-compressor. Fig. 9 is a perspective detail view ofa series of cooling-platesal; the same being in contact on both sides.

'--'-.thecooling-medium.' fFig. 17 shows suppleli ipes arranged between the cooling-plates and in intimate contact with the latter. Fig. 18 is a detail vertical section of a cooling device for an axial flow compressor. Fig. 19 is a detail section taken through one of the cooling channels.

20 is a detail horizontal section taken through Fig. 18. Fig. 21 is a detail verti cal section illustrating a series of secondary cooling plates. Fig. 22 is a detail transverse section of the same. Fig. 23 .is a detail horizontal section taken through Fig. 21. Fig. 24 is a detail vertical section of a modified form of the invention. Fig. 25 is a detail transverse section of the same. Fig. 26 is a detail horizontal section taken through Fig. 24.

The constructlon of a turbine of this kind is much simplified by constructing the cooling-device in such amanner that the cooling-plates replace the blades of the stator.

' In order to carry out this construction the blades are made of good heat conducting-material and connected to the annular coolingchannels 6. Different methods of uniting the cooling-channels with the cooling-plates may be employed, as for instance by casting or by means of galvanoplastic methods and by soldering them together.

- In Figs. 18, 19 and 20 I show a partof a 'coolin -device as mentioned before for an axialow-compressor. The coolingplates (Z are connected on two edges with the walls 7' of the cooling-channels and form at the same time the blades of the stator. An inlet and outlet for thecooling-medium and from the inner channel is effected by a few tubes or hollow blades 70. The heat of the surrounding gases is absorbed by the cooling-plates,

forming in this case the blades of the stator, and is conducted to the walls of the coolingchannels whence it enters into the coolingmedium. The space between the blades may be used for the reception of a series .of secondary coolingplates, as shown in Figs; 21, 22, and 23. The solid blades 1 of the axial-flow-turbine are in conductive connection with the cooling-plates d which are placed in parallel line to the direction of the gases to be compressed and represent the main cooling-surfaces. The cooling-plates 1 may be regarded as secondary ones, taking up the heat of the gases and communicating it to the blades d which are secured to the channels wheret-hrough the cooling-fluid passes. Answering to the intensity of the flow of theheat the cross sectional area of the blades or cooling-plates may gradually be increased to the spots where they are soldered or otherwise connected with the cooling-channels. The most favorable cooling effect, however, would be obtained if any or all of the blades are formed with hollow spaces for the passage of the coolingfluid and connected with each other by a series of secondary cooling-plates.

In Figs. 24, 25 and 26 I illustrate a somewhat modified form of the arrangement represented in the foregoing three figures. Referring to Fig. 24 and following Z designates a series of cooling-plates of annular form and d are hollow blades for the reception of the cooling-fluid communicating with the surrounding cooling-channels e. The heat absorbed by the cooling-plates is thus directly transferred to the blades (2 and thence to the cooling-medium.

1. In a turbo-compressor, the combination 105 of a rotor with a stator" and a cooling-device manufactured independently "of the compressor and additionally inserted in the gas-passages of said compressor, said cooling-device being fitted to the form of the 11 gas -channels'of said compressor and consisting of a series of thin, heat conducting plates, said plates being placed side by side and leaving small spaces for the passage of the gases to be compressed, and said heat 115 conducting plates being conductively connected with the walls of cooling-channels.

2. In a turbo-compressor, the combinationof a rotor witha stator and a cooling-device formed independently of the compressor and 120 additionally inserted in the gas-passages,

-said cooling-device being fitted to the form of the compressorand consisting of a series of thin, heat conducting plates, said plates being placed side by side and leaving small 126 spaces for the passage of the gases to be compressed, said heat conducting plates conductively secured on both edges lying in the direction of the flow of the gases to the walls. of cooling-channels. 13o

3. In a turbo-compressor, the combination of a rotor with a stator and a cooling-device formed independently of the compressor and additionally inserted in the gas-passages, said cooling-device being fitted to the form of the gas-channels of this compressor and consisting of a series of thin, heat conducting plates said plates being placed side by side and leaving small spaces for the passage of the gases to be compressed, and said heat conducting plates being secured to the walls of a cooling-channel.

4. In a turbo-compressor, the combination of a'rotor with a stator and a cooling-device formed independentlycof the compressor and additionally inserted in I the gas-passages, said cooling-device being fitted to the form of the gas-channels of the compressor and consisting of a series of thin, heat conducting plates, said plates being constructed in such a manner as to conduct these gases in a certain way and to make the arrangement of a special conducting-device dis ensable, said heat conducting plates con connected with the walls of cooling-channels,

5. In a'turbo-compressor, the combination of a rotor with a stator and a cooling-device.

mounted in the space formed between the blades of the stator, said cooling-device consisting of heat conducting plates, said plates being arranged parallelly to each other and uctively 4 leaving small spaces for the passage of the gases to be compressed, said heat conducting plates being arranged parallel to the flow of gases to prevent deflection of said gases, but to act as coolers, said heat conducting plates being secured to the walls ofthe blades of thestat-or, said walls being cooled by the fluid.

. 6. In a turbo-compressor, the combination of a rotor with a stator and a cooling-device mounted inthe space formed between the blades of the stator, said cooling-device consisting of heat conducting plates, said plates being arranged parallelly to each other leaving small spaces for the passage of the-gases to be compressed, these heat conducting plates being arranged so as to be unconnected with the task of the blades for conducting the gases in a certain way, but only act coolingly, said heat conducting plates being secured to the blades of the stator which latter are conductively con nected with the walls of cooling-channels,

In testimony whereof I have signed my name to' this specification in; the presence of two subscribing witnesses.

HUGO JUNKEns. Witnesses HENRY QUAnrmao', MATHIEU Gums. 

